A turbine blade of a gas turbine engine is described which includes an airfoil extending away from the hub platform to a blade tip. The airfoil defines a leading edge, a trailing edge, and a span-wise length extending between the platform and the blade tip. A hot-corrosion-resistant coating is located on the leading edge of the airfoil within a radially inner portion thereof, the radially inner portion extending away from the hub platform a desired distance along the span-wise length.

An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

A compressor housing for a turbocharger, which is composed of a scroll piece, a shroud piece, and an outer-circumferential annular piece. The scroll piece includes a through part constituting a discharge port, a first intermediate wall surface extended from an intake-side wall surface of a scroll chamber and smoothly connected with the discharge port, and a scroll outer-circumferential part. The outer-circumferential annular piece includes an outer-circumferential annular press-fit part press fitted into the scroll outer-circumferential part, and a protruding part bent from an outer-circumference-side wall surface of the scroll chamber. The protruding part is inserted into the through part to form an inner wall surface of an intermediate part that communicates the discharge port with the scroll chamber. Then, the compressor housing is fixed to a center housing that is made of iron with high rigidity through joining parts provided at the scroll piece.

A method for coating a substrate having a cavity structure, in particular a cooling structure, inside the substrate, wherein the cavity structure includes openings in the surface of the substrate. At least one bonding layer, in particular a diffusion layer, or at least one metallic layer is applied onto the substrate, in particular onto the surface of the substrate, and subsequently at least one thermal protection layer is applied onto the at least one diffusion layer by using a plasma spray physical vapour deposition (PS-PVD) method, a hollow cathode sputtering method or a suspension plasma spray (SPS) method.

A rocket engine has a combustion chamber having an inlet and an outlet, the inlet fluidly connectable to a source of oxidizer, the outlet in fluid communication with an environment outside the combustion chamber for expelling combustion gases, a first fuel having a first solid propellant and a second fuel having a second solid propellant, the first and second fuels located within the combustion chamber and configured to be exposed to the oxidizer injected in the combustion chamber via the inlet, the first solid propellant having a regression rate greater than that of the second solid propellant.

A pressure nitrided stainless steel hybrid ball bearing having an inner ring, an outer ring, and rolling elements disposed therebetween. The pressure nitrided stainless steel hybrid bearing has one or more component(s) made from a pressure nitrided stainless steel material. The pressure nitrided stainless steel hybrid bearing used with a refrigerant lubrication for chiller applications leads to a very long useful life time.

It is an objective of the invention to provide a steam turbine rotor of which a rotor shaft is made of a low-cost heat resistant ferritic steel and that can withstand high main steam temperatures of about 650 C. There is provided a steam turbine rotor comprising: a rotor shaft made of a heat resistant ferritic steel such as a 12-Cr steel; and a rotor blade made of a TiAl alloy, wherein the TiAl alloy includes: from 38 to 45 atomic % of Al; from 0.5 to 2 atomic % of V; from 2 to 6 atomic % of Cr and/or Mo; and the balance being Ti and incidental impurities.

An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed.

A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion.

An engine turning clock work motor including two shape memory alloy (SMA) torque tube actuators, ratcheting mechanisms, and gearing. The gearing communicates the SMA torque tube actuators with a common gear that applies torque to a shaft, so that while one torque tube is heated and applying torque, the other torque tube is relaxed (using a cooling mechanism). The ratchet prevents the relaxing torque tube from applying torque in the incorrect direction.